Combustor nozzle assembly, combustor equipped with the same, and gas turbine

Abstract

A combustor nozzle assembly includes: a nozzle mounting base which blocks a combustor insertion opening formed in a turbine casing; a nozzle rod which passes through the nozzle mounting base and has a rod tip portion and a rod base end portion; an oil fuel pipe which is as a whole inserted into the nozzle rod, which has a pipe tip portion and a pipe base end portion, in which fuel is supplied to the inside through the rod base end portion, and which injects the fuel from the pipe tip portion through the rod tip portion; and an O-ring which is disposed in the rod base end portion and suppresses leakage of fuel to the pipe tip portion side between the inner periphery side of the nozzle rod and the outer periphery side of the oil fuel pipe.

The invention claimed is: 
     
       1. A combustor nozzle assembly of a gas turbine comprising:
 a nozzle mounting base that blocks a combustor insertion opening formed in a turbine casing; 
 a nozzle rod formed in a tubular shape, passes through the nozzle mounting base, and having a rod tip portion protruding to an inside of the turbine casing and a rod base end portion protruding to the outside of the turbine casing; 
 a fuel pipe formed in a tubular shape, inserted as a whole into the nozzle rod, having a pipe tip portion fixed to the rod tip portion of the nozzle rod and a pipe base end portion inserted into the rod base end portion of the nozzle rod, wherein fuel is supplied to an inside of the fuel pipe through the rod base end portion, and injects the fuel from the pipe tip portion through the rod tip portion of the nozzle rod; and 
 a seal member disposed in the rod base end portion of the nozzle rod and suppresses leakage of the fuel to a pipe tip portion side between an inner periphery side of the nozzle rod and an outer periphery side of the fuel pipe, 
 wherein the nozzle rod comprises: 
 a mounting portion located in the nozzle mounting base; and 
 a cross-sectional area reduced portion provided between the mounting portion and the rod base end portion, wherein a cross-sectional area of the cross-sectional area reduced portion perpendicular to a direction that the nozzle rod extends is smaller than a maximum cross-sectional area of the mounting portion, and is also smaller than a cross-sectional area of the rod base end portion. 
 
     
     
       2. The combustor nozzle assembly of a gas turbine according to  claim 1 , wherein the cross-sectional area reduced portion of the nozzle rod is exposed to the outside of a combustor. 
     
     
       3. The combustor nozzle assembly of a gas turbine according to  claim 1 , wherein the rod base end portion of the nozzle rod is exposed to the outside of a combustor. 
     
     
       4. The combustor nozzle assembly of a gas turbine according to  claim 1 , further comprising:
 a fuel receiving pipe connected to the rod base end portion of the nozzle rod and supplies the fuel into the fuel pipe through the rod base end portion. 
 
     
     
       5. A combustor of a gas turbine comprising:
 the combustor nozzle assembly of a gas turbine according to  claim 1 ; and 
 a transition piece that leads combustion gas generated by burning of fuel injected from the pipe tip portion of the nozzle rod of the combustor nozzle assembly, to a turbine. 
 
     
     
       6. A gas turbine comprising:
 the combustor according to  claim 5 ; 
 a turbine rotor that is rotated by the combustion gas from the combustor; and 
 the turbine casing that covers the turbine rotor and wherein the combustor is mounted to the turbine casing.